![]() NACA 4 digit airfoil calculation The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber line. In the example XX=12 so the thiickness is 0 or 12% of the chord. In the example P=4 so the maximum camber is at 0 or 40% of the chord. In the example M=2 so the camber is 0 or 2% of the chord P is the position of the maximum camber divided by 10. NACA 2412 then: M is the maximum camber divided by 100. NACA 2412, which designate the camber, position of the maximum camber and thickness. 1 to 40% Number of points 81 20 to 200 Cosine spacing Cosine or linear spacing Close Trailing edge Open or closed TE Plot Send to airfoil plotter Add to comparison Add to My airfoils NACA 4 digit airfoils in the database NACA 0006 NACA 0008 NACA 0009 NACA 0010 NACA 0012 NACA 0015 NACA 0018 NACA 0021 NACA 0024 NACA 1408 NACA 1410 NACA 1412 NACA 2408 NACA 2410 NACA 2411 NACA 2412 NACA 2414 NACA 2415 NACA 2418 NACA 2421 NACA 2424 NACA 4412 NACA 4415 NACA 4418 NACA 4421 NACA 4424 NACA 6409 NACA 6412 NACA 4 digit airfoil specification This NACA airfoil series is controlled by 4 digits e. ![]() 0 to 90% Thickness (%) 12 Third & fourth digit. 0 to 9% Max camber position (%) 40 Second digit. (set) Search Dat file Applications Airfoil database search My airfoils Airfoil plotter Airfoil comparison Reynolds number calc NACA 4 digit generator NACA 5 digit generator Information Airfoil data Lift/drag polars Generated airfoil shapes Searches Symmetrical airfoils NACA 4 digit airfoils NACA 5 digit airfoils NACA 6 series airfoils Airfoils A to Z A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 (40) D dae11 to du861372 (28) E e1098 to esa40 (209) F falcon to fxs21158 (121) G geminism to gu255118 (419) H hh02 to ht23 (63) I isa571 to isa962 (4) J j5012 to joukowsk0021 (7) K k1 to kenmar (11) L l1003 to lwk80150k25 (24) M m1 to mue139 (95) N n0009sm to nplx (174) O oa206 to oaf139 (9) P p51droot to pw98mod (16) R r1046 to rhodesg36 (63) S s1010 to supermarine371ii (176) T tempest1 to tsagi8 (8) U ua2 to usnps4 (36) V v13006 to vr9 (17) W waspsm to whitcomb (4) Y ys900 to ys930 (3) List of all airfoils Site Home Contact Privacy Policy NACA 4 digit airfoil generator (NACA 2412 AIRFOIL) Max Camber (%) 2 First digit. parse: function(code): Parse the four-character String airfoil code, returning m (the amount of camber as a fraction of chord length), p (the location of maximum camber as a fraction of chord length), and t (thickness as a fraction of chord length).Airfoil Tools Search 1638 airfoils Tweet ThÃch 1,5K You have 0 airfoils loaded.Using the variables defined above, they are: ![]() The functions are also available as unadorned functions accessible on the plain module.
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